Research and Development of High-Efficiency Hall-Type Ion Engines for Small Spacecrafts

被引：0
|
作者：
Ikeda, Tomoyuki [1 ]
Sugimoto, Naru [1 ]
Togawa, Kazuya [1 ]
Mito, Yohei [1 ]
Tahara, Hirokazu [1 ]
机构：
[1] Osaka Inst Technol, Dept Mech Engn, Asahi Ku, Osaka 5358585, Japan
来源：
INTERNATIONAL CONFERENCE ON RENEWABLE ENERGY RESEARCH AND APPLICATIONS (ICRERA) | 2012年
关键词：
space propulsion; electric propulsion; Hall thruster; nano satellite; THRUSTER;
D O I：
暂无
中图分类号：
TE [石油、天然气工业]; TK [能源与动力工程];
学科分类号：
0807 ; 0820 ;
摘要：
Development of Hall thrusters for nano, small and low-power satellites below 100W is expected. In lowering Hall thruster power, the cylindrical-type Hall thruster is more advantage than conventional coaxial-type Hall thrusters. In this study, a very low power cylindrical Hall thruster was designed, and the thruster performance was measured. As a result, a stable operation was achieved even with 10W. The specific impulse and the thrust efficiency are 1570sec and 18.1%, respectively, with 66W. Also, the discharge current oscillation was lower compared SPT-type Hall thruster.
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页数：6
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